GAS TURBINE GROUPbarbosa/apresent _parcial... · 2020-02-13 · GAS TURBINE GROUP 2012. INSTITUTO TECNOLÓGICO DE AERONÁUTICA CENTER FOR REFERENCE ON GAS TURBINES Campus. ... Compressors

INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES

GAS TURBINE GROUP

2012


Campus


Campus


Center for Reference on Gas Turbines

Created after El Paso Rio Claro granted funds under special ANEEL permission to adequate an old building to house the Gas Turbine Group and

to provide computational resources to support research on gas turbines and gas turbines

applications


Laboratories




Professional MSc



Class rooms


Chemical Laboratory



Gas Turbine (PT6)Cutview



Collaborative Projects with the Aeronautical and Space Institute



Collaborative Projects with the Aeronautical and Space Institute


Gas TurbinePerformance Prediction (all types) Techonology and Power PlantsDeterioration and Faults Identification

Compressors and TurbinesAxial and CentrifugalWater Injection and Humid Air at Compressor InletDesign Optimization using genetic algorithms

Combustion ChambersDesign for Low Emission



Numerical MethodsCFDOptimizations of Computational CodesParalelization of Computational Codes

Noise PredictionSemi empirical methodsCFD-based

Turbine Blades Cooling

Corrosion and Thermal Barriers



Computational Codes Development:

• Gas Turbine Performance Prediction• Steady-State and Transient Regimes• Variable Geometry

• Compressors and Turbines Design and Performance Prediction• Gas and Steam turbines• Meanline Code - DP and ODP• Streamline Curvature Code (SLC) – DP and ODP



Computational Codes Development:

• CFD• Internal and/or External Flows in Turbomachinery

3-D Euler, viscous and turbulent flowsparallel version

• Combustion Chamber Design

• Fault Identification• using GPA, NL-GPA, Neural Networks, and Fuzzy Logic



Axial Compressor Meanline Code: VIGV + VSV + BOV + Different Loss Models

0,60

0,65

0,70

0,75

0,80

0,85

0,90

3,0 4,0 5,0 6,0 7,0 8,0 9,0 10,0 11,0

Mass Flow (kg/s)

Effic

ienc

y

Reference

AFCC

1st Analysis

2nd Analysis

3th Analysis

4th Analysis

0,0

2,0

4,0

6,0

8,0

10,0

12,0

14,0

0,0 2,0 4,0 6,0 8,0 10,0 12

Mass flow (kg/s)

Pres

sure

ratio



Axial Compressor Meanline Code: Optimization Model

Incidence Comparison (Optimized Compressor)

-2

0

2

4

6

8

10

12

14

1 2 3 4 5 6 7 8

Rotor

Inci

denc

e (º

)

nominalincidence

stallincidence

minimumlossincidence

calculatedincidence

Incidence Comparison (Optimized Compressor)

-2

0

2

4

6

8

10

12

14

1 2 3 4 5 6 7 8

Rotor

Inci

denc

e (º

)

nominalincidence

stallincidence

minimumlossincidence

calculatedincidence



Axial Compressor Meanline and Engine Performance Prediction Codes



Axial Compressor Meanline and Engine Performance Prediction Codes



Engine Transient Performance Prediction



3-Stage Axial Flow Compressor - SLC vs CFD

0102030405060708090

100

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6

% S

pan

Mach number

R1 inlet−SLCR1 inlet−CFD

0102030405060708090

100

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6

% S

pan

Mach number


0102030405060708090

100

0 0.2 0.4 0.6 0.8 1 1.2

% S

pan

Mach number




Axial Compressor Operating with Humid Air and Water Injection – SLC



CFD Code3-D, viscous, turbulent, RANS

Parallel version

Unstructured grid

Developed specially for application in turbomachines (compressor and turbine)

Full control of turbulence models, boundary conditions, initialization

Independence on software licenses

Platform for new developments



CFD Verification Cases



Airfoil withTransonic Flow and Nozzle with Supersonic Flow



Turbomachinery 3D CAD and Mesh Generation



Turbomachinery 3D Mesh Generation



Turbomachinery 3D Turbulent Flow Prediction

Total Pressure Distribution NGV (absolute values) and Rotor (relative values)

0

10

20

30

40

50

60

70

80

90

100

100000 150000 200000 250000 300000 350000 400000 450000 500000

Total Pressure [Pa]

% S

panw

ise

NGV LE: centered

NGV TE: centered

Rotor LE: centered

Rotor TE: centered

NGV LE: FDS

NGV TE: FDS

Rotor LE: FDS

Rotor TE: FDS




Total Temperature Distribution NGV (absolute values) and Rotor (relative values)

0

10

2030

40

50

60

7080

90

100

900 925 950 975 1000 1025 1050 1075 1100 1125 1150 1175 1200

Total Temperature [k]

% S

panw

ise

Rotor TE: centered

Rotor TE: FDS

Outlet: centered

Outlet: FDS




Mach number Distribution NGV (absolute values) and Rotor (relative values)

0

10

20

30

40

50

60

70

80

90

100

0 0,2 0,4 0,6 0,8 1 1,2

Mach number

% S

panw

ise

NGV LE: S-A

NGV TE: S-A

Rotor LE: S-A

Rotor TE: S-A

NGV LE: SST

NGV TE: SST

Rotor LE: SST

Rotor TE: SST




Total Pressure Distribution - Inter-Blade RowsNGV (absolute values) and Rotor (relative values)

0102030405060708090

100

100000 200000 300000 400000 500000

Total Pressure [Pa]

% S

panw

ise

NGV MPlane: 5 div

Rotor MPlane: 5 div

NGV MPlane: 10 div

Rotor MPlane: 10 div

NGV MPlane: L-B-L

Rotor MPlane: L-B-L












Turbofan Nacelle = Design and 3D Turbulent Flow Prediction



Reverser Cascade Design for Turbofan Engine



Paralelization of CFD Computational Code



Paralelization of CFD Computational Code



Preliminary Centrifugal Compressor Design and Stress Prediction

'



Neural Networks and Optimization Studies



Engine Performance - Variation of Turbine Blade Cooling with Different TIT



Project TAPP – Gas Generator Vibration and Lubrification Test StandFINEP and TGM Turbinas



Project TAPP – Data Acquisition SoftwareFINEP and TGM Turbinas



Turbojet: 5.0 kNTurboprop: 1.2 MW

Project TAPP – View of internal configurationFINEP and TGM Turbinas


Documents

GAS TURBINE GROUPbarbosa/apresent _parcial... · 2020-02-13 · GAS TURBINE GROUP 2012. INSTITUTO TECNOLÓGICO DE AERONÁUTICA CENTER FOR REFERENCE ON GAS TURBINES Campus. ... Compressors